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RD-861
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 | RD-861
Credit - © Dietrich Haeseler
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Manufacturer Name: RD-861. Government Designation: 11D25. Other Designations: S5.23, D-25. Designer: Yangel. Developed in: 1968-72. Application: Tsyklon 2 and 3 stage 3; Ikar. Propellants: N2O4/UDMH. Thrust(vac): 78.710 kN (17,695 lbf). Isp: 317 sec. Burn time: 130 sec. Mass Engine: 123 kg (271 lb). Diameter: 1.53 m (5.01 ft). Length: 1.56 m (5.11 ft). Chambers: 1 + 4 + 2. Chamber Pressure: 88.80 bar. Area Ratio: 112.40. Oxidizer to Fuel Ratio: 2.10. Thrust to Weight Ratio: 65.25. Country: Ukraine. Status: In production. First Flight: 1965. Last Flight: 2006. Flown: 229. Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. Mass given in ref. IAF-97-S.1.04 is 162 kg instead of 123 kg originally stated.
RD-861 used on Rocket Stages
Bibliography and Further Reading - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...
- Shnyakin, V N, Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye, GKB Yuzhnoe "Yangel", Dnepropetrovsk 1996 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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